Solid propellant rocket stage. Loaded/empty mass 278,330/38,200 kg. Thrust 6,470.00 kN. Vacuum specific impulse 275 seconds. Increased propellant loading (+2.43 tonnes), lighter welded case (-1.6 tonnes) compared to earlier versions.
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Status: In development.
Gross mass: 278,330 kg (613,610 lb).
Unfuelled mass: 38,200 kg (84,200 lb).
Height: 31.60 m (103.60 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 6,470.00 kN (1,454,510 lbf).
Specific impulse: 275 s.
Specific impulse sea level: 250 s.
Burn time: 130 s.
Number: 52 .
P241 SEP solid rocket engine. 6470 kN. In development. Isp=275s. First flight 2002. More...
Associated Launch Vehicles
Ariane 5 V French orbital launch vehicle. Version of the evolved Ariane 5 using a version of the EPS storable propellant stage instead of a new Lox/LH2 stage. Result is a payload to GTO of 8 tonnes. The use of the new Aestus restartable engine in the upper stage fitted the vehicle for space station logistics missions or launch of space probes requiring complex orbital maneouvres. More...
Ariane 5 EC-B French orbital launch vehicle. The ultimate evolved Ariane 5 funded as of the end of the millenium. A larger Lox/LH2 upper stage using the Vinci motor in place of the HM7B. The core remains the same. Result is an increase in GTO payload from 10.5 tonnes to 12.0 tonnes. More...
Ariane 5ECA French orbital launch vehicle, first version of the evolved Ariane 5. The solid booster motors propellant load was increased by 2.43 tonnes and the case was welded, for a weight saving in dry mass of 1.9 tonnes. The core was powered by an improved Vulcain 2 engine. The oxygen-rich cycle of the engine allowed the oxygen bulkhead to be moved within the stage, resulting in a 15.2 tonne increase in propellant in the core. A new Lox/LH2 upper stage, using the HM7B engine and oxygen tank from the Ariane 4 series, replaced the storable propellant EPS stage of earlier models. The result was an increase in payload to geoscynchronous transfer orbit from 6 tonnes to 10.5 tonnes. More...
Ariane 5ES Version of the Ariane 5 designed to orbit ESA's Automated Transfer Vehicle (ATV) resupply vehicle for the International Space Station. More...
Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...
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